CN103967650A - Turbofan engine - Google Patents
Turbofan engine Download PDFInfo
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- CN103967650A CN103967650A CN201310656435.7A CN201310656435A CN103967650A CN 103967650 A CN103967650 A CN 103967650A CN 201310656435 A CN201310656435 A CN 201310656435A CN 103967650 A CN103967650 A CN 103967650A
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- fan
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- flow compressor
- turbine
- pressure ratio
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Abstract
A turbofan engine comprises all structures of a turbofan engine such as a fan, an outer duct, an axial-flow air compressor, an evaporative combustion chamber, a turbine and a tail jet pipe. The turbojet engine is characterized in that a bypass pipe and an inner exhaust valve are further included, an outer exhaust valve is arranged or not arranged on the bypass pipe between an air inlet and an air outlet of the bypass pipe, after the engine is started and operates, the inner exhaust valve is opened, by opening and closing of the bypass pipe, the inner exhaust valve and the existing or nonexistent outer exhaust valve, the supercharge ratio of the axial-flow air compressor or the fan is increased and kept unchanged, the increased supercharge ratio is not higher than the limitation borne by the fan, the axial-flow air compressor and a turbine according to the mechanical strength, turbine inlet temperature is kept unchanged, namely the supercharge ratio and thrust-weight ratio are increased, oil consumption rate is lowered, the levels of the fan, the axial-flow air compressor and the turbine are not increased, and the turbine inlet temperature is not raised.
Description
Technical field
The present invention relates to a kind of turbofan engine, is a kind of turbofan engine that improves pressure ratio and thrust weight ratio specifically, belongs to particularly military turbofan engine technical field of turbofan.
Background technique
In turbofan engine, the pressure ratio that improves fan, axial-flow compressor can increase thrust, improve pressure ratio, is mainly at present fuel gas temperature before increasing the progression of fan, axial-flow compressor, turbine or improving turbine; But the former increases weight and volume, unfavorable to improving thrust weight ratio, GE90 as used in Boeing 777, PW4084 and Rui Da 800 turbofan engines, the progression of its gas compressor, turbine is more, and pressure ratio, total pressure ratio are higher, but thrust weight ratio is not high; Latter must use turbine blade material high temperature resistant, that performance is good, cladding material and advanced cooling technology, as M88, EJ200, F119 use advanced material and the cooling technologies such as monocrystal material, crystallizing materials, improving before turbine 150 DEG C of fuel gas temperatures more than-200 DEG C than previous generation military turbofan engine, is very difficult but continue to improve; And the pressure ratio of current turbofan engine is all fixed, cannot change and improve.
Summary of the invention
The object of this invention is to provide a kind of not increasing any one progression in fan, axial-flow compressor, turbine, do not improve in the situation of the front fuel gas temperature of turbine, improve the pressure ratio of fan and axial-flow compressor, thereby improve the turbofan engine of thrust weight ratio, reduction oil consumption rate.
The present invention is achieved in that turbofan engine, comprise fan, by-pass air duct, axial-flow compressor, evaporation-combustion chamber, turbine, all structures of the turbofan engines such as jet pipe, in jet pipe, can have or without afterburning fuel nozzle, it is characterized in that also comprising bypass tube, its suction port is after axial-flow compressor and between before evaporation-combustion chamber, by between them after engine start and axial-flow compressor pressure ratio lower than improve after pressure ratio time open, improving the exhaust gas inside valve of closing after axial-flow compressor pressure ratio is connected with main duct, its air outlet is after fan, before axial-flow compressor, towards axial-flow compressor suction port, axial-flow compressor improve after pressure ratio not higher than fan, the limit that the mechanical strength of axial-flow compressor, turbine is born.
Turbofan engine, comprise all structures of the turbofan engines such as fan, by-pass air duct, axial-flow compressor, evaporation-combustion chamber, turbine, jet pipe, it is characterized in that also comprising bypass tube, its suction port is after fan or after fan, before axial-flow compressor, by be positioned at fancase after engine start and fan forced ratio lower than improve after pressure ratio time open, improve the exhaust gas inside valve of closing after fan forced ratio and be connected with after fan, its air outlet or towards engine intake; The limit that fan forced ratio after raising does not bear higher than the mechanical strength of fan, axial-flow compressor, turbine.
Described fan is single-stage fan.
Described fan is more than single-stage or multistage fan.
In bypass tube between described bypass tube air inlet/outlet without the outside exhaust valve of adjutage compressed air pressure.
In bypass tube between described bypass tube air inlet/outlet, there is the outside exhaust valve of adjutage compressed air pressure.
Adopt after said structure, owing to there being bypass tube, in bypass tube between exhaust gas inside valve and bypass tube air inlet/outlet, also have or the outside exhaust valve of nothing, while operation after engine start, exhaust gas inside valve is opened, send a part of pressurized air after axial-flow compressor or after fan back to axial-flow compressor or engine intake by bypass tube, together with airborne air inlet, increase its suction pressure from air inlet or the motor of fan with axial-flow compressor, continuously compress through axial-flow compressor or fan, evaporation-combustion chamber work by combustion, compressed air pressure after compression all will increase gradually, in the time that the compressed air pressure after compression increases to needing of pressure ratio after axial-flow compressor or fan improve, exhaust gas inside valve is closed, only with motor from airborne air inlet and without the air inlet of bypass tube, therebetween can with or need not the compressed air pressure in bypass tube be regulated outside exhaust valve, then in using, the operation that the open and close of outside exhaust valve or exhaust gas inside valve keep the constant continuation motor of pressure ratio after raising, and before maintenance turbine, fuel gas temperature is constant, the limit that pressure ratio after raising is not born higher than the mechanical strength of fan, axial-flow compressor, turbine, be that pressure ratio, thrust weight ratio improve, oil consumption rate reduces, but the progression of fan, axial-flow compressor, turbine do not increase, and before turbine, fuel gas temperature does not improve.
Brief description of the drawings
Below in conjunction with drawings and Examples, the present invention is explained in detail:
Fig. 1 is first structural representation of turbofan engine of the present invention.
Fig. 2 is second structural representation of turbofan engine of the present invention.
Fig. 3 is the 3rd structural representation of turbofan engine of the present invention.
Fig. 4 is the 4th structural representation of turbofan engine of the present invention.
Fig. 5 is the 5th structural representation of turbofan engine of the present invention.
Fig. 6 is the 6th structural representation of turbofan engine of the present invention.
Fig. 7 is the 7th structural representation of turbofan engine of the present invention.
Fig. 8 is the 8th structural representation of turbofan engine of the present invention.
Embodiment
With reference to accompanying drawing 1 to 8, turbofan engine of the present invention comprises fan 1, by-pass air duct 2, axial-flow compressor 3, bypass tube 4, exhaust gas inside valve 5, evaporation-combustion chamber 6, turbine 7, jet pipe 8 etc.; Its fan 1 can be single-stage, as shown in Figures 1 to 4; Also can be single-stage above or multistage, as shown in Fig. 5 to Fig. 8; Fan 1, axial-flow compressor 3 are connected by axle with turbine 7 respectively; The suction port of bypass tube 4 can be after axial-flow compressor 3 and between before evaporation-combustion chamber 6, be connected with main duct by the exhaust gas inside valve 5 between them, its air outlet is after fan 1, before axial-flow compressor 3 and towards axial-flow compressor 3 suction ports, as shown in Fig. 1,2,5,6; The suction port of bypass tube 4 also can be after fan 1 or after fan 1, before axial-flow compressor 3 suction ports, be connected with after fan 1 by the exhaust gas inside valve 5 that is positioned at fan 1 casing, its air outlet or towards engine intake, as shown in Fig. 3,4,7,8; Can be without the outside exhaust valve 9 of adjutage compressed air pressure in bypass tube between bypass tube 4 air inlet/outlets, as shown in Fig. 1,3,5,7, also can be just like shown in Fig. 2,4,6,8; In jet pipe 8, can have or without afterburning oil nozzle.
In the time that described turbofan engine is the turbofan engine shown in Fig. 1 to Fig. 8 of the present invention, while operation after startup, exhaust gas inside valve 5 is opened, by also having between bypass tube 4, exhaust gas inside valve 5 and bypass tube 4 air inlet/outlets or the open and close of the outside exhaust valve 9 of nothing, the pressure ratio of axial-flow compressor 3 or fan 1 is improved and increases and remain unchanged, and keep the front fuel gas temperature of turbine 7 constant, its process as mentioned before; No matter be to improve fan 1 or the pressure ratio of axial-flow compressor 3, their two pressure ratios all can be enhanced; In the present embodiment, axial-flow compressor 3 or fan 1, owing to there being the effect of cyclotron in physics in the combination of running state and bypass tube 4, can be that pressure ratio improves easily by the air pressure after compression in theory.
In the present embodiment, the progression of axial-flow compressor 3, turbine 7 can be selected as required; The quantity of bypass tube 4 is 1 to multiple; Exhaust gas inside valve 5, outside exhaust valve 9 can be the air bleed valves that meets the current known various structures of service condition; Wherein in Fig. 2, Fig. 6, bypass tube 4 and outside exhaust valve 9 can be in by-pass air ducts 2, also can be outside body, and the decisions such as the pressure ratio after the exhaust pressure of outside exhaust valve 9 improves according to fan 1 or axial-flow compressor 3; The present invention can be used for current particularly military turbofan engine of various turbofan engines.
Claims (6)
1. turbofan engine, comprise fan (1), by-pass air duct (2), axial-flow compressor (3), evaporation-combustion chamber (6), turbine (7), all structures of the turbofan engines such as jet pipe (8), it is characterized in that also comprising bypass tube (4), its suction port after the axial-flow compressor (3) and evaporation-combustion chamber (6) front between, by between them after engine start and axial-flow compressor (3) pressure ratio lower than improve after pressure ratio time open, improving the exhaust gas inside valve (5) of closing after axial-flow compressor (3) pressure ratio is connected with main duct, its air outlet is after fan (1), axial-flow compressor (3) is front, towards axial-flow compressor (3) suction port, the limit that pressure ratio after axial-flow compressor (3) improves is not born higher than the mechanical strength of fan (1), axial-flow compressor (3), turbine (7).
2. turbofan engine, comprise fan (1), by-pass air duct (2), axial-flow compressor (3), evaporation-combustion chamber (6), turbine (7), all structures of the turbofan engines such as jet pipe (8), it is characterized in that also comprising bypass tube (4), its suction port is after fan (1) or after fan (1), before axial-flow compressor (3) suction port, by be positioned at fan (1) casing after engine start and fan (1) pressure ratio lower than improve after pressure ratio time open, improving the exhaust gas inside valve (5) of closing after fan (1) pressure ratio is connected with after fan (1), its air outlet or towards engine intake, the limit that pressure ratio after fan (1) improves is not born higher than the mechanical strength of fan (1), axial-flow compressor (3), turbine (7).
3. turbofan engine according to claim 1 and 2, is characterized in that described fan (1) is single-stage fan.
4. turbofan engine according to claim 1 and 2, is characterized in that described fan (1) is more than single-stage or multistage fan.
5. turbofan engine according to claim 1 and 2, is characterized in that the outside exhaust valve (9) without adjutage compressed air pressure in the bypass tube between described bypass tube (4) air inlet/outlet.
6. turbofan engine according to claim 1 and 2, is characterized in that having in the bypass tube between described bypass tube (4) air inlet/outlet the outside exhaust valve (9) of adjutage compressed air pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310656435.7A CN103967650A (en) | 2013-01-24 | 2013-12-09 | Turbofan engine |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310026191 | 2013-01-24 | ||
| CN201310026191.4 | 2013-01-24 | ||
| CN201310656435.7A CN103967650A (en) | 2013-01-24 | 2013-12-09 | Turbofan engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103967650A true CN103967650A (en) | 2014-08-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310656435.7A Pending CN103967650A (en) | 2013-01-24 | 2013-12-09 | Turbofan engine |
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| CN (1) | CN103967650A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105089850A (en) * | 2015-05-27 | 2015-11-25 | 何仲华 | Space aircraft carrier engine |
| CN108278165A (en) * | 2017-12-14 | 2018-07-13 | 雷静桃 | A kind of adjustable aero-engine of the direction of motion |
| CN109324528A (en) * | 2018-09-19 | 2019-02-12 | 中国航发湖南动力机械研究所 | Culvert type turboshaft engine, turboshaft engine duct control system and control method |
| CN114878175A (en) * | 2022-04-15 | 2022-08-09 | 中国航发沈阳发动机研究所 | Outer culvert area synchronous adjusting mechanism of inner and outer culvert diversion exhaust system |
-
2013
- 2013-12-09 CN CN201310656435.7A patent/CN103967650A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105089850A (en) * | 2015-05-27 | 2015-11-25 | 何仲华 | Space aircraft carrier engine |
| CN108278165A (en) * | 2017-12-14 | 2018-07-13 | 雷静桃 | A kind of adjustable aero-engine of the direction of motion |
| CN109324528A (en) * | 2018-09-19 | 2019-02-12 | 中国航发湖南动力机械研究所 | Culvert type turboshaft engine, turboshaft engine duct control system and control method |
| CN114878175A (en) * | 2022-04-15 | 2022-08-09 | 中国航发沈阳发动机研究所 | Outer culvert area synchronous adjusting mechanism of inner and outer culvert diversion exhaust system |
| CN114878175B (en) * | 2022-04-15 | 2024-02-23 | 中国航发沈阳发动机研究所 | Outer culvert area synchronous regulating mechanism of inner culvert and outer culvert split-flow exhaust system |
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Application publication date: 20140806 |